DE601527T1 - System for checking the higher harmonic vibrations in the rotor blades of a helicopter. - Google Patents

System for checking the higher harmonic vibrations in the rotor blades of a helicopter.

Info

Publication number
DE601527T1
DE601527T1 DE0601527T DE93119661T DE601527T1 DE 601527 T1 DE601527 T1 DE 601527T1 DE 0601527 T DE0601527 T DE 0601527T DE 93119661 T DE93119661 T DE 93119661T DE 601527 T1 DE601527 T1 DE 601527T1
Authority
DE
Germany
Prior art keywords
cylinder
hhc
rotor blade
force
higher harmonic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
DE0601527T
Other languages
German (de)
Inventor
Wilmer H Reed
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Dynamic Engineering Inc
Original Assignee
Dynamic Engineering Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Dynamic Engineering Inc filed Critical Dynamic Engineering Inc
Publication of DE601527T1 publication Critical patent/DE601527T1/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/56—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
    • B64C27/57—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/001—Vibration damping devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/72—Means acting on blades
    • B64C2027/7205—Means acting on blades on each blade individually, e.g. individual blade control [IBC]
    • B64C2027/7261—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps
    • B64C2027/7294—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps actuated mechanically, e.g. by means of linkages
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/30—Wing lift efficiency
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Catching Or Destruction (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Vibration Prevention Devices (AREA)
  • Wind Motors (AREA)
  • Apparatuses For Generation Of Mechanical Vibrations (AREA)

Abstract

Higher harmonic control (hereinafter HHC) of helicopter rotor blade vibrations is provided by an actively controlled, rotatable, slotted cylinder (11) which is mounted at an outboard section of each blade (12). Continuous rotation of each cylinder (11) about its longitudinal axis produces a periodic aerodynamic force on the blade (12) at a frequency of twice the rotational frequency of the cylinder. The amplitude of force is controlled by the size of a slot opening (110,111,112,133) in the cylinder while the rotational speed of the cylinder is synchronized to run at a multiple of the speed of a rotor blade drive shaft. The amplitude and phase of the HHC force is regulated, either manually or by active feedback control, to minimize any vibratory load transmitted to the airframe through the rotor blade drive shaft. A significant advantage offered by this concept, relative to other HHC methods, is its low power requirement. <IMAGE>
DE0601527T 1992-12-11 1993-12-07 System for checking the higher harmonic vibrations in the rotor blades of a helicopter. Pending DE601527T1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/989,583 US5314308A (en) 1992-12-11 1992-12-11 System for controlling higher harmonic vibrations in helicopter rotor blades

Publications (1)

Publication Number Publication Date
DE601527T1 true DE601527T1 (en) 1995-04-06

Family

ID=25535244

Family Applications (2)

Application Number Title Priority Date Filing Date
DE69310111T Expired - Fee Related DE69310111T2 (en) 1992-12-11 1993-12-07 System for checking the higher harmonic vibrations in the rotor blades of a helicopter
DE0601527T Pending DE601527T1 (en) 1992-12-11 1993-12-07 System for checking the higher harmonic vibrations in the rotor blades of a helicopter.

Family Applications Before (1)

Application Number Title Priority Date Filing Date
DE69310111T Expired - Fee Related DE69310111T2 (en) 1992-12-11 1993-12-07 System for checking the higher harmonic vibrations in the rotor blades of a helicopter

Country Status (11)

Country Link
US (1) US5314308A (en)
EP (1) EP0601527B1 (en)
JP (1) JPH072187A (en)
KR (1) KR940014085A (en)
CN (1) CN1092727A (en)
AT (1) ATE152062T1 (en)
DE (2) DE69310111T2 (en)
DK (1) DK0601527T3 (en)
ES (1) ES2060576T3 (en)
GR (2) GR940300078T1 (en)
TW (1) TW239107B (en)

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DE19528155C1 (en) * 1995-08-02 1996-06-27 Deutsche Forsch Luft Raumfahrt Helicopter rotor blade of glass fibre reinforced synthetic resin
US5973440A (en) 1997-07-07 1999-10-26 Nitzsche; Fred Structural component having means for actively varying its stiffness to control vibrations
EP0936140A4 (en) * 1997-09-10 2002-07-10 Inst Adv Tech Helicopter Ltd Rotor control system
FR2770826B1 (en) * 1997-11-07 2000-01-07 Eurocopter France ROTOR BLADE WITH ADJUSTABLE SHUTTER
DE10035333B4 (en) * 2000-07-20 2008-08-14 Eads Deutschland Gmbh Rotor blade with control flaps
DE10052757A1 (en) * 2000-10-25 2002-05-08 Zf Luftfahrttechnik Gmbh Rotor blade control device
US6493689B2 (en) 2000-12-29 2002-12-10 General Dynamics Advanced Technology Systems, Inc. Neural net controller for noise and vibration reduction
US6671590B1 (en) 2001-04-30 2003-12-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method and system for active noise control of tiltrotor aircraft
CA2454575C (en) * 2001-08-02 2009-02-24 Bell Helicopter Textron Inc. Helicopter main rotor blade balance weight retention assembly
FR2871435B1 (en) 2004-06-10 2006-08-18 Eurocopter France DEVICE FOR INDICATING A BEAT LEVEL
US7448854B2 (en) 2004-08-30 2008-11-11 Lord Corporation Helicopter vibration control system and rotary force generator for canceling vibrations
US7722322B2 (en) 2004-08-30 2010-05-25 Lord Corporation Computer system and program product for controlling vibrations
US8435002B2 (en) 2004-08-30 2013-05-07 Lord Corporation Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations
US8267652B2 (en) 2004-08-30 2012-09-18 Lord Corporation Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations
US8162606B2 (en) 2004-08-30 2012-04-24 Lord Corporation Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations
DE102005007129B4 (en) * 2005-02-17 2008-07-10 Zf Friedrichshafen Ag Device for controlling rotor blades of a helicopter
US7648338B1 (en) 2006-09-14 2010-01-19 Sikorsky Aircraft Corporation Dual higher harmonic control (HHC) for a counter-rotating, coaxial rotor system
KR101486721B1 (en) 2007-10-25 2015-01-28 로드코포레이션 Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations
FR2929253B1 (en) 2008-03-28 2013-09-13 Sartorius Stedim Biotech Sa RIGID FRAME FOR 3D CONTAINER CONTAINING AT LEAST PARTIALLY DEFORMABLE
US8985068B2 (en) 2010-07-22 2015-03-24 Robert Bosch Gmbh Systems and methods for avoiding resonances excited by rotating components
KR101911000B1 (en) 2011-02-04 2018-10-23 로오드 코포레이션 Rotary wing aircraft vibration control system with resonant inertial actuators
WO2013120103A1 (en) 2012-02-10 2013-08-15 Appareo Systems, Llc Frequency-adaptable structural health and usage monitoring system
US10607424B2 (en) 2012-02-10 2020-03-31 Appareo Systems, Llc Frequency-adaptable structural health and usage monitoring system (HUMS) and method with smart sensors
US9816529B2 (en) 2013-03-15 2017-11-14 Kcf Technologies, Inc. Propeller sound field modification systems and methods
US9394045B2 (en) 2013-03-15 2016-07-19 Kcf Technologies, Inc. Propeller sound field modification systems and methods
JP6469389B2 (en) * 2014-08-29 2019-02-13 三菱航空機株式会社 Aircraft vibration system and aircraft
CN104670492B (en) * 2015-01-23 2016-11-16 南京航空航天大学 A kind of helicopter blade embedded radial motion shimmy damper
IL240316B (en) 2015-08-03 2018-10-31 Technion Res & Dev Foundation Method and system for parametric amplification
US20170129597A1 (en) * 2015-11-10 2017-05-11 Sikorsky Aircraft Corporation Reduced power individual blade control system on a rotorcraft
DE102016213720A1 (en) 2016-07-26 2018-02-01 Zf Friedrichshafen Ag System for data transmission and processing for controlling a rotor blade actuator
US11299263B2 (en) 2016-12-07 2022-04-12 Textron Innovations Inc. Automatic, active blade tracking and balance system
CN108639335B (en) * 2018-04-04 2020-06-02 北京航空航天大学 Flexible deformation system of helicopter rotor aileron for vibration and noise control
CN113955142B (en) * 2021-10-09 2023-09-05 中国直升机设计研究所 Rotor wing 1 omega harmonic vibration real-time adjustment control method
CN115056979B (en) * 2022-07-01 2023-05-23 南京航空航天大学 Active vibration control method and system based on periodic motion of rotor wing shimmy direction

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US1785333A (en) * 1926-11-18 1930-12-16 Trey Serge Helicopter
FR855833A (en) * 1939-06-07 1940-05-21 Device for producing a force resulting from the flow of a fluid especially for airplanes
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Also Published As

Publication number Publication date
DE69310111T2 (en) 1997-08-07
TW239107B (en) 1995-01-21
GR3023986T3 (en) 1997-10-31
ES2060576T3 (en) 1997-06-16
ES2060576T1 (en) 1994-12-01
EP0601527B1 (en) 1997-04-23
CN1092727A (en) 1994-09-28
JPH072187A (en) 1995-01-06
ATE152062T1 (en) 1997-05-15
EP0601527A1 (en) 1994-06-15
DK0601527T3 (en) 1997-10-27
US5314308A (en) 1994-05-24
GR940300078T1 (en) 1994-11-30
DE69310111D1 (en) 1997-05-28
KR940014085A (en) 1994-07-16

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